Investigation of the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel

Abstract

Tapered wing featuring aspect ratio of 9.0 and NACA 65-210 airfoil section was tested at rates of flow of up to Mach 0.925. Radical changes of zero lift angles and normal-force-curve slope during Mach variation and different angles of attack are reviewed. Outboard shift in lateral centers of load were established to produce increase of approximately 5% in bending moment at wing root. Negative-pitch-moment-coefficient fluctuation, drag coefficient, and wake dimensions are analyzed.

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Document Details

Document Type
Technical Report
Publication Date
Aug 28, 1946
Accession Number
ADB815264

Entities

People

  • Richard T. Whitcomb

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airfoils
  • Aspect Ratio
  • Bending Moments
  • Boundary Layer
  • Coefficients
  • Dynamic Pressure
  • Leading Edges
  • Mach Number
  • Measurement
  • Outboard
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.